Abstract: Ultrasonic systems and methods for inspecting a channel member through a skin or panel are provided. The channel member may be a stiffener for an aircraft component such as a trapezoidal stringer attached to a skin of an aircraft fuselage. Transducers of the system are disposed on a side of the skin opposite the channel member. Ultrasonic waves generated on a first side of a skin propagate through the skin, across a channel member attached to a second side of the skin, and through the skin again to be received on the first side of the skin. Times of flight are measured for the collection of time-gated data. A two dimensional C-scan is generated for identifying flaws and irregularities in a structure by way of single-side ultrasonic non-destructive inspection (NDI).

Abstract: A system and method for determining whether an aircraft is ready to fly or should be repaired in light of damage and/or malfunction information observed at the departure gate includes observing damage or malfunction, alerting decision-makers, and initiating an automated interview session via a camera equipped communications device to a remote server running query driven decision and data analysis software. Data entered via the communications device, equipped with a keypad and camera for obtaining visual information, is transmitted to the remotely based software application. The software generates requests for information based on prior received information, processes and provides the information to decision-makers at remote locations. The communications device transmits decision-making support information concerning repair or dispatch. The communication device may be a wireless cell phone with a digital camera.

Abstract: An NDI system includes an ultrasonic transducer and an electronic device having an indicator, such as a light source. The electronic device energizes the transducer, receives sinusoidal signals from the transducer, determines impedance-plane coordinates corresponding to quadrature-phase separated components of the sinusoidal signals, and automatically activates the indicator if impedance-plane coordinates exceed a preset threshold. The system may be used in methods of inspecting layered structures such as composite aircraft components and repair patches applied to such structures.

Abstract: Systems and methods are disclosed for providing nondestructive inspection (NDI) services. For example in accordance with an embodiment of the invention, a system for remote inspection includes a nondestructive inspection (NDI) system configured to examine a structure and provide NDI data related to a damage condition of the structure, the NDI system being configured to communicate the NDI data to a remote location; and a remote computer disposed at the remote location, the remote computer being configured to receive the NDI data and provide the received NDI data for a review, the remote computer being configured to communicate an analytical result based on the review to the NDI system, the analytical result including a repair disposition decision corresponding to the damage condition.

Abstract: First and second thermal sensors measure the respective temperatures of portions of a surface of a structure such as an aircraft component. An alert signal is emitted if the temperatures of the surface portions are substantially different. An energy source causes heat flow within the structure. Subsurface flaws such as disbonded areas between composite layers and foreign materials obstruct heat flow within the structure and cause proximate surface portions to exhibit different temperatures. A non-alert signal may be emitted if the temperatures of proximate surface portions are essentially the same.

Abstract: An ultrasonic inspection reference standard for a composite material includes a block comprising the composite material. The block further comprises a first plurality of parallel rectangular-shaped channels within the block and a second plurality of parallel rectangular-shaped channels within the block, wherein the second plurality of channels extend at about a ninety degree angle to the first plurality of channels and wherein the second plurality of channels is located on a separate plane as the first plurality of channels.

Abstract: Techniques for ultrasonically evaluating damage to a laminate structure include use of a diagnostic device having at least two modes of operation including a calibration mode and a test mode with the calibration mode providing calibration parameters specific to the laminate structure under test.

Abstract: A non-destructive method determines an amount of heat exposure to a resin-fiber composite substrate. A value of infrared energy reflected by a composite substrate is determined. The value of infrared energy reflected, or conversely absorbed, is correlated to a degree or amount of heat exposure. According to an aspect of the present invention, one method utilizes an infrared spectrometer to determine infrared absorbance of a composite substrate. The infrared energy of the reflected beam is then compared with the pre-determined value of infrared energy reflected off a reference heat damaged composite substrate to determine the amount of heat exposure.

Abstract: The apparatus and method for moving a sensor over a workpiece includes a sensor, and an actuating member. The sensor, such as a non-destructive test sensor, is carried by the actuating member, and the actuating member is at least partially disposed within a housing. The actuating member is adapted for automated movement in one direction, and the housing may be configured to be grasped by an operator and manually moved in another direction. As such, the sensor may automatically move in one direction with respect to the workpiece without manual intervention, and manually move in another direction, such that the sensor is moved by the combination of automated and manual movement. In addition, the actuating member may have at least two substantially parallel arms extending from near the sensor, which permits the sensor to slide along the workpiece while maintaining a substantially normal relationship to a surface of the workpiece.

Abstract: A damage detection device is used to detect damage in bonded and laminated composite structures. A tap hammer or tap coin containing an acceleration sensor is connected to a circuit that can measure the width of an impact signal and then display the result. The result correlates to local stiffness of a structure. A method of determining the desired signal width and the method of using the damage detection device, includes tapping a known good region and then tapping a suspect region. Readings from the two areas are used to determine whether the suspect region is within an acceptable range. The circuit determines the desired signal width by measuring from the time the impact signal exceeds a threshold to the time it falls below the threshold.

Abstract: The apparatus and method for moving a sensor over a workpiece includes a sensor, and an actuating member. The sensor, such as a non-destructive test sensor, is carried by the actuating member, and the actuating member is at least partially disposed within a housing. The actuating member is adapted for automated movement in one direction, and the housing may be configured to be grasped by an operator and manually moved in another direction. As such, the sensor may automatically move in one direction with respect to the workpiece without manual intervention, and manually move in another direction, such that the sensor is moved by the combination of automated and manual movement. In addition, the actuating member may have at least two substantially parallel arms extending from near the sensor, which permits the sensor to slide along the workpiece while maintaining a substantially normal relationship to a surface of the workpiece.